EP0846845B1 - Paire d'aubes de rotor et rotor comportant une telle paire d'aubes - Google Patents

Paire d'aubes de rotor et rotor comportant une telle paire d'aubes Download PDF

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Publication number
EP0846845B1
EP0846845B1 EP97309780A EP97309780A EP0846845B1 EP 0846845 B1 EP0846845 B1 EP 0846845B1 EP 97309780 A EP97309780 A EP 97309780A EP 97309780 A EP97309780 A EP 97309780A EP 0846845 B1 EP0846845 B1 EP 0846845B1
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EP
European Patent Office
Prior art keywords
blade pair
airfoil
fibers
airfoils
rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP97309780A
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German (de)
English (en)
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EP0846845A2 (fr
EP0846845A3 (fr
Inventor
Alfred Paul Matheny
Chen Yu J. Chou
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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Filing date
Publication date
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Publication of EP0846845A2 publication Critical patent/EP0846845A2/fr
Publication of EP0846845A3 publication Critical patent/EP0846845A3/fr
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Publication of EP0846845B1 publication Critical patent/EP0846845B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction

Definitions

  • the present invention relates to gas turbine engine rotor assemblies in general, and to rotor blades in particular.
  • Axial turbine engines generally include fan, compressor, combustor and turbine sections positioned along an axial centerline sometimes referred to as the engines "axis of rotation".
  • the fan, compressor, and combustor sections add work to air (also referred to as "core gas") flowing through the engine.
  • the turbine extracts work from the core gas flow to drive the fan and compressor sections.
  • the fan, compressor, and turbine sections each include a series of stator and rotor assemblies.
  • the stator assemblies which do not rotate (but may have variable pitch vanes), increase the efficiency of the engine by guiding core gas flow into or out of the rotor assemblies.
  • the rotor assemblies typically include a plurality of blades attached to and extending out from the circumference of a disk. It is known to attach rotor blades to a disk by "fir tree" blade roots or the like, received in complementary shaped recesses within the disk. A disadvantage of a "fir tree” type attachment scheme is that the disk must be sized relatively large to accommodate the stresses generated by the blades acting on the disk. Specifically, the disk must have sufficient area between adjacent recesses to handle the shear load placed on the recesses by the mating roots of the rotor blades. Another method of rotor blade attachment involves using a pin to hold the rotor blades to the disk.
  • the blade root of each blade necks down to a lug having an aperture for receiving a pin.
  • the lug is received between flanges extending out from the disk.
  • the pin extends through the disk flanges and blade lug to secure the blade to the disk.
  • the entire load on the blade is borne by the pin, which in turn transfers the load to the disk flanges.
  • the cross-sectional area of the pin must be substantial and the disk must have adequate web material between adjacent pin apertures. Typically, adequate web material is attained by moving the pin apertures radially outward.
  • the substantial pin diameter and radial position of the pin apertures often lead to a rotor disk having a weight and an internal flow path diameter greater than optimum.
  • US 5,273,401 discloses a lightweight bladed rotor for gas turbine engines.
  • US 3,597,109 discloses a gas turbine engine aixal flow multistage compressor, comprising rotor blade members mounted on a plurality of platform elements disposed radially outwardly of and spaced from a rotor member.
  • a rotor blade pair for attachment to a rotor disk which includes a platform, a first and a second airfoil, and a root having a first and second wall.
  • the platform has an inner and an outer radial surface.
  • the first and second airfoils extend out from the outer radial surface of the platform.
  • the root walls extend out from the inner radial surface of the platform, and are integrally connected to one another, forming a hollow between the walls and the inner radial surface.
  • the first wall is substantially aligned with the first airfoil and the second wall is substantially aligned with the second airfoil.
  • the first and second airfoils, and the aligned first and second walls of the root are skewed from the axial centerline of the engine.
  • the first and second airfoils spiral around an axis extending between the forward and aft edges of each airfoil.
  • the first and second walls of the root spiral around an axis extending between the forward and aft edges of the root, an amount substantially equal to that of the airfoils, thereby maintaining the alignment between the airfoils and the walls of the root.
  • a particular embodiment of the invention comprises first fibres extending from adjacent the tip of one airfoil through the first airfoil, through said first and second root walls, through the second airfoil to adjacent the tip of the second airfoil. It further preferably comprises second fibres adjacent the first fibres and having a modulus of elasticity lower than the first fibres. The second fibres preferably have a higher percentage of elongation at failure than the first.
  • Preferred embodiments of the invention include damping means to dissipate energy caused by foreign object impacts.
  • damping means may comprise an interblade region of the platform which includes the aforementioned second fibres.
  • An advantage of the present invention is that a rotor blade pair is provided having a significant radial load capability.
  • One factor contributing to the radial load capability of the present rotor blade pair is the alignment of the airfoils with the root walls. Alignment between an airfoil and a blade root wall permits the radial pull lines ("radial pull line” is a term of art used to describe the force vectors extending through an airfoil) of the airfoil to continue into the blade root and thereby minimize stresses elsewhere in the blade pair.
  • the airfoils and root walls are aligned regardless of the orientation of the airfoils relative to the platform; i.e., airfoils spiraling out of the platform, or being skewed from the axial centerline of the engine, or both.
  • Another factor contributing to the radial load capacity of the present invention rotor blade pairs are the first fibers extending from airfoil to airfoil, via the root. The continuous first fibers connecting the airfoils to the blade root reinforce the blade pair and thereby increase the radial load capability.
  • Another advantage of the present invention is its ability to withstand foreign object damage.
  • the platform of the present invention is designed to dissipate energy delivered by foreign objects impacting one or both blade pair airfoils.
  • Another advantage of the present invention is that a lightweight rotor blade assembly is provided.
  • the present invention rotor blade assembly avoids a solid rotor disk and heavy alloy rotor blades.
  • an axial turbine engine 10 includes a fan section 12 which has a plurality of inlet guide vanes 16, a first rotor stage 18, a first stator stage 20, a second rotor stage 22, a second stator stage 24, and a third rotor stage 26, positioned forward to aft respectively. Forward is defined as being upstream of aft.
  • the inlet guide vanes 16 and the stator stages 20, 24 guide air into, or out of, the rotor stages 18,22,26.
  • the first, second, and third rotor stages 18,22,26 rotate about the axial centerline 28 of the engine 10.
  • a spool 30 powered by a downstream turbine (not shown) drives the fan rotor stages 18,22,26.
  • the first rotor stage 18 includes a rotor disk 32 and a plurality of rotor blade pairs 34, distributed around the circumference of the disk 32.
  • each rotor blade pair 34 includes a first airfoil 36, a second airfoil 38, a platform 40, and a root 42.
  • the platform 40 has a forward edge 44, an aft edge 46, an outer radial surface 48, and an inner radial surface 50.
  • the airfoils 36,38 are spaced apart and substantially parallel to one another, and extend out from the outer radial surface 48 of the platform 40.
  • the root 42 of each blade pair 34 includes a first 52 and a second 54 root wall, integrally attached to one another, extending out from the inner radial surface 50 of the platform 40.
  • the hollow 56 formed between blade root walls 52,54 has a cross-sectional geometry similar to that of the rotor disk stub shafts 86,98 (discussed in more detail hereinafter).
  • the airfoils 36,38 are skewed from the axial centerline 28 by an angle " ⁇ " which extends between the chord line of the airfoils 36,38 and the axial centerline 28.
  • the blade pair airfoils 36,38 spiral in a compound manner between the base 58 and the tip 60, and between the forward 62 and aft 64 edges, of each airfoil 36,38.
  • the airfoil spirals almost exclusively around an axis extending between the forward 62 and aft 64 edges.
  • the base 58 to tip 60 component of the airfoil spiral increases with radial position away from the base 58, and is therefore less significant at the base 58.
  • the airfoils 36,38 do not intersect the platform 40 along a constant plane.
  • Each blade root wall 52,54 is substantially aligned with one of the airfoils 36,38 and consequently spirals in a manner equal to, or nearly equal to, that of the airfoil 36,38.
  • the blade root walls 52,54 like the airfoils 36,38, may have small anomalies that deviate from the symmetry of the blade root walls 52,54.
  • the angle " ⁇ " shown in FIG.5 illustrates the amount of spiral within the blade root 42 between the forward 66 and aft 68 edges of the blade root 42.
  • the blade pairs 34 are fabricated from composite materials which include a plurality of first 72 and second 73 fibers disposed within a composite matrix.
  • the first fibers 72 extend from, or near, the tip 60 of one airfoil 36,38 down through the platform 40, into one blade root wall 52,54, up through the other blade root wall 54,52, back through the platform 40, and into the other airfoil 38,36, terminating at or near the tip 60.
  • the second fibers 73 are positioned adjacent the first fibers 72, extending along the airfoils 36,38 and root 42.
  • the second fibers 73 also extend throughout the platform 40.
  • second fibers 73 can extend from a section of platform 40 into a blade root wall 52,54, or from the platform 40 into an airfoil 36,38, or from one airfoil 36,38 through the platform interblade region 70, and into the other airfoil 38,36.
  • the first fibers 72 have a Modulus of Elasticity value higher than that of the second fibers 73, and are therefore "stiffer" than the second fibers 73.
  • the second fibers 73 however, have a higher percentage of elongation at failure than the first fibers 72.
  • the distribution of the first 72 and second 73 fibers within the blade pair 34 and the mechanical properties of the first 72 and second 73 fibers give the blade pair 34 desirable performance characteristics.
  • the alignment between the airfoils 36,38 and blade root walls 52,54 enables the first fibers 72 to extend in a continuous manner through out the blade pair 34.
  • the radial pull lines extend linearly, or nearly linearly, through each airfoil 36,38 and its aligned blade root wall 52,54, which in turn optimizes the load capacity of the blade pair 34.
  • the interblade region 70 thus acts as a damper.
  • Lower energy foreign object impacts are accommodated by allowing the energy of the impact to transfer into and dissipate within the platform 40, thereby minimizing the damage to the airfoil(s) 36,38 and root 42.
  • Higher energy foreign object impacts are also accommodated by transferring the energy of the impact into the platform 40. If the impact energy is great enough, however, the platform will partially or completely buckle and fail while dissipating the energy of the impact.
  • the platform 40 is sacrificed, if necessary, to keep the airfoils 36,38 attached, which in turn minimizes further damage within the engine 10.
  • the constituent material of the first 72 and second 73 fibers will depend upon the application at hand. Carbon fibers and glass fibers are examples of first and second fiber materials, respectively.
  • the rotor disk 32 includes a forward web 74 and an aft web 76.
  • the forward web 74 includes an inner surface 78, a forward spool attachment member 80, a forward flange 82, a center hub 84, and a plurality of first stub shafts 86.
  • the inner surface 78 is disposed at an angle " ⁇ " relative to a radial line 80 perpendicular to the axial centerline 28.
  • the first stub shafts 86 are distributed around the circumference of the forward web 74, extending out from the inner surface 78.
  • Each first stub shaft 86 extends lengthwise between an axial end 88 and a web end 90.
  • the web end 90 of each first stub shaft 86 is preferably integrally attached, by a metallurgical bond for example, to the inner surface 78 of the forward web 74.
  • the aft web 76 includes an inner surface 92, an aft spool attachment member 94, a center hub 96, and a plurality of second stub shafts 98.
  • the inner surface 92 of the aft web 76 is disposed at an angle " ⁇ " relative to a radial line 100 perpendicular to the axial centerline 28.
  • the second stub shafts 98 are distributed around the circumference of the aft web 76, extending out from the inner surface 92.
  • Each second stub shaft 98 extends lengthwise between an axial end 102 and a web end 104.
  • the web end 104 of each second stub shaft 98 is preferably integrally attached, by a metallurgical bond for example, to the inner surface 92 of the aft web 76.
  • each first and second stub shaft 86,98 are equal in number, and similarly spaced around the axial centerline 28. Each first stub shaft 86 aligns with a second stub shaft 98, and vice versa.
  • a plurality of fasteners 106 such as nut and bolt pairs, attach the first and second stub shafts 86,98, and therefore the webs 74,76, to one another.
  • each first and second stub shaft 86,98 includes a flange 108 adjacent the axial end 88,102, extending out from the outer radial surface 110 of the stub shaft 86,98.
  • the flanges 108 of the aligned stub shafts 86,98 align with one another, and the fasteners 106 couple the aligned stub shafts 86,98 through the flanges 108.
  • the first and second stub shafts 86,98 may also include mating surfaces 112 disposed in the axial end 88,102 of each shaft 86,98.
  • FIGS. 1 and 9, illustrate one embodiment of the mating surfaces 112 where each first and second stub shaft 86,98 includes a tongue 114 extending into the other shaft 98,86.
  • Other mating surfaces 112 may be used alternatively.
  • the stub shafts 86,98 extend between the forward 74 and aft 76 webs, skewed from the axial centerline 28 and spiraling between webs 74,76 in a manner similar to that of the blade roots 42 described above.
  • the amount of skew between the stub shafts 86,98 and the axial centerline 28 is substantially equal to the skew between the chord lines of the airfoils 36,38 and the axial centerline 28 and is, therefore, represented by the same angle " ⁇ ".
  • the amount of spiral (or “twist") along the length of the combined stub shafts 86,98 is likewise shown as angle " ⁇ ", heretofore described as the amount of spiral within the blade pair root 42.
  • the skew angle " ⁇ " and spiral angle “ ⁇ ” magnitudes will depend upon the application at hand. An advantage of the present invention is that a variety of skew angles and degrees of spiral can be accommodated, thereby giving the present invention considerable versatility.
  • the fan section 12 is assembled by receiving the first stub shafts 86 in the blade root hollows 56 of an appropriate number of rotor blade pairs 34.
  • the second stub shafts 98 are inserted into the hollows 56 and aligned with the first stub shafts 86.
  • the inner surfaces 78,92 of the forward 74 and aft 76 webs disposed at angles " ⁇ " and " ⁇ " respectively, maintain the blade pairs 34 in position and thereby facilitate assembly.
  • the fasteners 106 are subsequently inserted into the flanges 108 on the outer radial surface 110 of the stub shafts 86,98 and tightened to attach the stub shafts 86,98, and therefore the webs 74,76, together.
  • the present invention provides an axial turbine engine rotor assembly that has a minimal internal flow path diameter, and is of minimal weight.
  • the present invention rotor assembly is described herein as a fan rotor assembly.
  • the present invention rotor assembly may be used in compressor and/or turbine applications alternatively.
  • the blade pairs 34 are described above as being composite structures.
  • the blade pairs are not limited, however, to composite materials.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (14)

  1. Paire d'aubes de rotor (34), destinée à être fixée à un disque rotor, pour tourner autour d'un axe, comprenant :
    une plateforme (40), présentant une surface radiale interne et externe (50, 48) ;
    une emplanture (42) ;
    une première surface portante (36), s'étendant en dehors de ladite surface radiale externe (48) de ladite plateforme (40) ;
    une seconde surface portante (38), s'étendant en dehors de ladite surface radiale externe (48) de ladite plateforme (40) ;
       dans laquelle chacune desdites surfaces portantes présente un bord avant (62), un bord arrière (64), une base (58) et une pointe (60) ; et
       dans laquelle ladite emplanture (42) est caractérisée par :
    une première paroi (52), une seconde paroi (54), un bord avant (66), et un bord arrière (68), lesdites parois s'étendant en dehors de ladite surface radiale interne (50) de ladite plateforme (40), et étant reliées intégralement l'une à l'autre, formant un creux (56) entre lesdites parois (52, 54) et ladite surface radiale interne (50) ;
       dans laquelle ladite première paroi (52) est sensiblement alignée avec ladite première surface portante (36), et ladite seconde paroi (54) est sensiblement alignée avec ladite seconde surface portante (38).
  2. Paire d'aubes de rotor selon la revendication 1, dans laquelle lesdites première et seconde surfaces portantes (36, 38), et lesdites première et seconde parois alignées (52, 54) de ladite emplanture (42) sont obliques par rapport à l'axe.
  3. Paire d'aubes de rotor selon la revendication 1 ou 2, dans laquelle lesdites première et seconde surfaces portantes (36, 38) s'étendent en dehors de ladite surface radiale externe (48), de manière sensiblement parallèle l'une par rapport à l'autre, et lesdites première et seconde parois (52, 54) de ladite emplanture (42), alignées avec lesdites première et seconde surfaces portantes (36, 38), s'étendent en dehors de ladite surface radiale externe (50), de manière sensiblement parallèle l'une par rapport à l'autre.
  4. Paire d'aubes de rotor selon la revendication 3, dans laquelle lesdites première et seconde surfaces portantes (36, 38), et lesdites première et seconde parois alignées (52, 54) de ladite emplanture (42) sont obliques par rapport à l'axe.
  5. Paire d'aubes de rotor selon la revendication 4, dans laquelle lesdites première et seconde surfaces portantes (36, 38) vont en spirale autour d'un axe s'étendant entre lesdits bords avant et arrière (62, 64) de chacune desdites surfaces portantes.
  6. Paire d'aubes de rotor selon la revendication 5, dans laquelle lesdites première et seconde parois (52, 54) de ladite emplanture (42) vont en spirale autour d'un axe s'étendant entre lesdits bords avant et arrière de ladite emplanture selon une valeur sensiblement égale à celle desdites surfaces portantes (36, 38), maintenant ainsi ledit alignement entre lesdites surfaces portantes et lesdites parois de ladite emplanture.
  7. Paire d'aubes de rotor selon l'une quelconque des revendications précédentes, comprenant en outre :
    une pluralité de premières fibres (72), s'étendant d'un endroit adjacent à ladite pointe (60) de ladite première surface portante (36), à travers ladite première surface portante (36), jusque dans et à travers lesdites première et seconde parois (52, 54), et à travers ladite seconde surface portante (38), s'étendant jusqu'à un point adjacent de ladite pointe (60) de ladite seconde surface portante (38).
  8. Paire d'aubes de rotor selon la revendication 7, comprenant en outre :
    une pluralité de secondes fibres (73), s'étendant d'un point adjacent auxdites premières fibres (72), et disposées à l'intérieur de ladite plateforme (40) ;
       dans laquelle lesdites secondes fibres (73) présentent une valeur de module d'élasticité inférieure à celle desdites premières fibres (72).
  9. Paire d'aubes de rotor selon la revendication 8, dans laquelle lesdites secondes fibres (73) présentent un pourcentage d'allongement à la rupture supérieur à celui desdites premières fibres (72).
  10. Paire d'aubes de rotor selon la revendication 1, comprenant en outre :
    un amortisseur, ledit amortisseur dissipant l'énergie transférée à ladite paire d'aubes par un objet étranger percutant l'une desdites surfaces portantes.
  11. Paire d'aubes de rotor selon la revendication 8, comprenant en outre :
    un amortisseur, ledit amortisseur dissipant l'énergie fournie à ladite paire d'aubes (34) par un objet étranger percutant l'une desdites surfaces portantes.
  12. Paire d'aubes de rotor selon la revendication 11, dans laquelle ledit amortisseur comprend :
    une région (70) entre les aubes de ladite plateforme (40), dans laquelle ladite région entre les aubes comprend lesdites secondes fibres (73).
  13. Paire d'aubes de rotor selon la revendication 12, dans laquelle lesdites secondes fibres (73) présentent un pourcentage d'allongement à la rupture supérieur à celui desdites premières fibres (72).
  14. Ensemble formant rotor comprenant une pluralité de paires d'aubes (34), selon l'une quelconque des revendications précédentes, fixées à un disque rotor (32).
EP97309780A 1996-12-04 1997-12-04 Paire d'aubes de rotor et rotor comportant une telle paire d'aubes Expired - Lifetime EP0846845B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/759,827 US5735673A (en) 1996-12-04 1996-12-04 Turbine engine rotor blade pair
US759827 2001-01-12

Publications (3)

Publication Number Publication Date
EP0846845A2 EP0846845A2 (fr) 1998-06-10
EP0846845A3 EP0846845A3 (fr) 2000-05-10
EP0846845B1 true EP0846845B1 (fr) 2005-11-09

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EP97309780A Expired - Lifetime EP0846845B1 (fr) 1996-12-04 1997-12-04 Paire d'aubes de rotor et rotor comportant une telle paire d'aubes

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US (1) US5735673A (fr)
EP (1) EP0846845B1 (fr)
JP (1) JPH10169403A (fr)
KR (1) KR100497697B1 (fr)
DE (1) DE69734560T2 (fr)

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Also Published As

Publication number Publication date
EP0846845A2 (fr) 1998-06-10
KR100497697B1 (ko) 2005-09-08
KR19980063735A (ko) 1998-10-07
EP0846845A3 (fr) 2000-05-10
DE69734560T2 (de) 2006-05-24
DE69734560D1 (de) 2005-12-15
US5735673A (en) 1998-04-07
JPH10169403A (ja) 1998-06-23

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